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Supplier: Accuris
Description: HANDBOOK, OVERHAUL INSTRUCTIONS (LIQUID PROPELLANT ROCKET ENGINES)
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Supplier: Accuris
Description: Reliability Demonstration of Liquid Propellant Rocket Engines
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Description: practices with new tools capable of reducing the volume of resources and the time required to complete simulations and analysis. This book presents an innovative parametric model applicable to the project of some elements of the liquid rocket thrust chamber with the level of detail and
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Supplier: SAE International
Description: . For example, new liquid rocket engine programs, such as the joint NASA/Air Force effort for the National Launch System (NLS) or the Air Force XLR-132 storable propellant upper stage engine, include documented requirements for high levels of reliability. These new requirements
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Supplier: Accuris
Description: ROCKET ENGINE, LIQUID PROPELLANT, GENERAL SPECIFICATION FOR
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Supplier: Accuris
Description: TANK, REMOVABLE, LIQUID PROPELLANT ROCKET ENGINE, GENERAL SPECIFICATION FOR
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Supplier: ASTM International
Description: 1.1 Purpose-The purpose of this guide shall be to provide fundamental safeguards for the storage, use, and handling of liquid rocket propellants to ensure the safety of workers involved as well as the public. 1.2 Goal-The functional goal of this guide shall be to reduce the
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Supplier: CSA Group
Description: ISO 16694:2015 applies to all types of liquid rocket engines for expendable launch systems and satellites: a) Combustible fuel (including cryogenic); b) Large-thrust, multiple component engines, with and without afterburning; c) Low-thrust engines, one component (mono-propellant
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Supplier: ASTM International
Description: 1.1 This practice covers the evaluation of the compatibility of nitrogen tetroxide (N 2 O 4 ) rocket engine propellant with materials which will be used in aerospace systems. The practice includes immersion procedures in the vapor phase, liquid phase, critical vapor, and
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GENERAL PLASTICS’ POLYURETHANE FOAM FILLS KEY ROLE IN GROUND TEST OF WORLD’S LARGEST SOLID ROCKET MOTOR (read more)
Browse Foams and Foam Materials Datasheets for General Plastics Manufacturing Co. -
Now more than ever it is important to monitor and control it's output. Nitrous oxide (N2O) is also known as “laughing gas”. It is not just used in medicine. It is also used in the food industry as a propellant for spray whipped cream (E 942), in (read more)
Browse Gas Sensors Datasheets for Electro Optical Components, Inc. -
used in modern industry. Rocket propellants, cryogenic fuels, and pressurized gases require rigorous monitoring from storage through launch. Hydrogen, for example, is highly flammable and difficult to detect (read more)
Browse Gas Sensors Datasheets for DOD Technologies Inc. -
. Liquid Fuel Management RP-1 Kerosene, Hydrazine Nitrogen Tetroxide (NTO) Jet Fuels High Temperature Rocket Engine Sealing Hybrid Hydrogen Aerospace Engine Sealing Flow Control New Energies Oil (read more)
Browse Metal Ring Seals Datasheets for Technetics Group -
grade robots / drones, engine components and fuel pumps for airplanes, fleets, rockets, jets, etc. Certified: Meet DFARS, REACH and RoHS requirements. Pressure-tested to military standard 1,500 psi. American Made: (read more)
Browse Screws Datasheets for ZAGO Manufacturing Company, Inc. -
-tech self-sealing fasteners are engineered with a groove under the head of the fastener or in the face of the nut that when combined with a rubber O-ring and tightened, forms a leak-proof seal against the incursion and expulsion of liquids and gasses, including fuel. Weather and (read more)
Browse Switch Sealing Boots Datasheets for ZAGO Manufacturing Company, Inc. -
molding methods and is used in the manufacture of such things as piping, stacks, chemical storage tanks and rocket motor casings. Because tooling costs for open molds tend to be lower, open molding is more widely used for short production runs. It’s typically used for larger (read more)
Browse Mold Making Services Datasheets for Osborne Industries, Inc. -
dissolve these barriers, operating with more precision than everyday descaling agents like citric acid. Oxidation accelerates when metals heat up. Aluminum, for example, oxidizes many times faster at 300°C. Flux creates a liquid shield akin to a non-stick coating on a frying pan, minimizing oxygen (read more)
Browse Welding, Brazing, and Soldering Equipment Datasheets for ODG (Origin Data Global) -
required to carry liquefied gases at cryogenic temperatures down to minus 269 degrees Celsius. Aircraft tubing may transfer cryogenic sensor coolants, supercooled jet fuel or liquid oxygen in a rocket engine. Austenitic stainless steels and some aluminum alloys are suitable for cryogenic service (read more)
Browse Medical Tubing Datasheets for Eagle Stainless Tube & Fabrication, Inc. -
Trimmer Calibrate liquid flow Aerospace (read more)
Browse Wirewound Resistors Datasheets for ODG (Origin Data Global)
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Metal 3D Printing and Machining Produce High-Efficiency Rocket Designed by Stanford Students
. The organization supports a variety initiatives that range from biology and high-altitude balloons to satellites and rocketry. One group of students is heading up a project solely dedicated to creating a liquid propellant rocket with the goal of setting the world record for altitude reached
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Powered Flight
With respect to straightforward operation, in a typical SRM, there is no throttling (modulated feed of fuel and/or oxidizer to adjust thrust delivery, as might be done in a hybrid or liquid pro- pellant rocket engine), although on occasion, one sees the …
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Rocketing Into the Future
Liquid propellant rockets have a lower weight relative to their thrust and, unlike solids, can be throttled up or down, and even stopped entirely without blowing up.
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Computation of Viscous Incompressible Flows
Three separate chapters are devoted to simulations of liquid propellant rocket engine sub- systems, turbopumps, and hemodynamics related to simulation of blood circulation in the human brain and in mechanical heart assist devices.
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Modern Engineering for Design of Liquid-Propellant Rocket Engines > Design of Thrust Chambers and Other Combustion Devices
For a more detailed description of instability characteristics and analysis procedures, consult NASA SP-194, " Liquid Propellant Rocket Combustion Instability." .
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Modern Engineering for Design of Liquid-Propellant Rocket Engines > Introduction to Liquid-Propellant Rocket Engines
Assume a thrust chamber for the same ideal liquid propellant rocket engine as given in Sample Cal- culation 1-2, in which Wtc = 360.7 Ib/s; (Pc)ns=1000 psia; (Tc)ns=6540°R; M = 22.67; y =1.20; and e =12.
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Design of liquid-propellant rocket engines
In developing liquid propellant rocket engines, the trend is to reduce the guaranteed reserves of fuel and to eliminate the guaranteed reserves of booster fuel.
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Rocket and Spacecraft Propulsion
Liquid propellant rocket engines . . . . . . . . . . . . . . . . . . . . . . . . . .
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Rocket and Spacecraft Propulsion
3 Liquid propellant rocket engines . . . . . . . . . . . . . . . . . . . . . . . . . . .